# Boeing Alert Service Bulletin 757-27A0157: No revision named

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- Document: [Boeing Alert Service Bulletin 757-27A0157](https://openairdocs.org/service-documents/boeing/757-27a0157.md)
- Title as filed: SB-757-27A0157 rev Original dated 12 18 17
- Pages: 49
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## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-27A0157
Original Issue: December 18, 2017
ATA System: 2760
SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings -
New Spoiler Control Module Relay Wiring Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: December 18, 2017
757-27A0157
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Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 17
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 20
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL  [Group 1-3, Configuration 1] . . . . . . . . . . 33
FIGURE 2: W1265 WIRE BUNDLE ROUTING  [Group 1-3, Configuration 1] . . . . . . . . . . . . . . 36
FIGURE 3: W1265 WIRE BUNDLE CHANGES  [Group 1-3, Configuration 1] . . . . . . . . . . . . . . 39
FIGURE 4: W1265 WIRE BUNDLE CHANGES  [Group 1, Configuration 1] . . . . . . . . . . . . . . . 41
FIGURE 5: W1265 WIRE BUNDLE CHANGES  [Group 2-3, Configuration 1] . . . . . . . . . . . . . . 42
FIGURE 6: W1265 WIRE BUNDLE CHANGES  [Group 1-3, Configuration 1] . . . . . . . . . . . . . . 43
FIGURE 7: E3-1 ELECTRONICS SHELF - INSTALLATION  [Group 1-3, Configuration 1] . . . . . . . 45
APPENDIX A: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
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Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-27A0157Original Issue: December 18, 2017
ATA System: 2760
SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings -
New Spoiler Control Module Relay Wiring Change
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will make sure that the changes given in Boeing Service Bulletin
757-27A0152, that prevent the deployment of spoiler pairs 1 and 12 and 5 and 8 during landing operations, are
deactivated. If the SB is not done it will leave the airplane at risk for a potential failure mode that can cause an
uncommanded spoiler movement that can put the airplane into excessive lateral control resulting in loss of
controllability of the airplane.
Boeing has received a report that a 757 operator that had accomplished Boeing Service Bulletin 757-27A0152,
had experienced a momentary uncommanded spoiler movement when configuring the flaps just before landing.
Boeing Service Bulletin 757-27A0152 gives protection to reduce the chance of a Pilot Induced Oscillation (PIO)
on airplanes when the pilot is trying to make quick flight maneuvers, such as the final phase of landings in strong
wind conditions. However, subsequent investigation of Boeing Service Bulletin 757-27A0152 has identified a
failure effect that could result in uncommanded spoiler movement that could lead to loss of controllability of the
airplane.
This service bulletin gives instructions to deactivate the changes given in Boeing Service Bulletin 757-27A0152.
Boeing Service Related Problem (SRP) 757-SRP-27-0290 is related to this service bulletin.
Boeing Multi-Operator Message MOM-MOM-17-0685 is related to this service bulletin.
ACTION
Group 1-3, Configuration 1:
Get access to the Electronic Equipment Bay (E/E Bay). Remove the E3-1 electronics shelf from the airplane if
necessary. Make changes to wire bundle W1265. Install the E3-1 electronics shelf to the airplane, if removed,
and do a test of the Spoiler/Speedbrake Control System. Close access.
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Group 1-3, Configuration 2:
No work is necessary for these airplanes.
EFFECTIVITY
757-200, -200CB, -200PF, -300 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the test procedures given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
GROUP 1-3, CONFIGURATION 1:
E3-1 ELECTRONICS SHELF:
-REMOVE ELECTRONICS SHELF. IF NECESSARY.
-CHANGE WIRE BUNDLE W1265.
-INSTALL ELECTRONICS SHELF, IF REMOVED.
-DO A TEST OF THE SPOILER/SPEEDBRAKE
CONTROL SYSTEM.
MAIN EQUIPMENT CENTER
M531
M530
O
W1265
E3-1 ELECTRONICS SHELF
(TYPICAL)
2802959
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Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-27A0157
Original Issue: December 18, 2017
ATA System: 2760
SUBJECT: FLIGHT CONTROLS - Spoiler, Drag Devices and Variable Aerodynamic Fairings -
New Spoiler Control Module Relay Wiring Change
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 757-200, -200CB, -200PF, -300 airplanes, line numbers 002
thru 1050 in 3 Groups. The Variable Numbers and Group Information for the applicable airplanes
is given below.
DESCRIPTIONCONFIGURATIONGROUP
757-200, -200CB, -200PF airplanes.-1
Airplanes that have accomplished service bulletin 757-27A0152.1
Airplanes that have not accomplished service bulletin 757-27A0152.2
757-300 airplanes.-2
Airplanes that have accomplished service bulletin 757-27A0152.1
Airplanes that have not accomplished service bulletin 757-27A0152.2
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DESCRIPTIONCONFIGURATIONGROUP
757-200, -300 airplanes with wiring configuration differences.-3
Airplanes that have accomplished service bulletin 757-27A0152.1
Airplanes that have not accomplished service bulletin 757-27A0152.2
Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300
GroupVariable Number
1NA002 - NA028
1NA191 - NA199
1NA201 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
1NA401 - NA408
1NA441 - NA447
1NA501 - NA586
1NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
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GroupVariable Number
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
1NB321 - NB331
1NB421 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1NC901 - NC951
1NC971 - NC974
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE008
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GroupVariable Number
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
3NJ001 - NJ004
3NJ031 - NJ032
3NJ551 - NJ555
2NL001
3NL002
2NL006 - NL017
3NL101 - NL109
3NL141
3NL601 - NL616
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
1NS601 - NS616
1NT001 - NT009
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
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GroupVariable Number
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
2NU701 - NU705
2NU721 - NU728
2NU731 - NU732
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will make sure that the changes given in Boeing Service Bulletin
757-27A0152, that prevent the deployment of spoiler pairs 1 and 12 and 5 and 8 during landing
operations, are deactivated. If the SB is not done it will leave the airplane at risk for a potential failure
mode that can cause an uncommanded spoiler movement that can put the airplane into excessive
lateral control resulting in loss of controllability of the airplane.
Boeing has received a report that a 757 operator that had accomplished Boeing Service Bulletin
757-27A0152, had experienced a momentary uncommanded spoiler movement when configuring the
flaps just before landing. Boeing Service Bulletin 757-27A0152 gives protection to reduce the chance
of a Pilot Induced Oscillation (PIO) on airplanes when the pilot is trying to make quick flight maneuvers,
such as the final phase of landings in strong wind conditions. However, subsequent investigation of
Boeing Service Bulletin 757-27A0152 has identified a failure effect that could result in uncommanded
spoiler movement that could lead to loss of controllability of the airplane.
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This service bulletin gives instructions to deactivate the changes given in Boeing Service Bulletin
757-27A0152.
Boeing Service Related Problem (SRP) 757-SRP-27-0290 is related to this service bulletin.
Boeing Multi-Operator Message MOM-MOM-17-0685 is related to this service bulletin.
D. Description
Group 1-3, Configuration 1:
Get access to the Electronic Equipment Bay (E/E Bay). Remove the E3-1 electronics shelf from the
airplane if necessary. Make changes to wire bundle W1265. Install the E3-1 electronics shelf to the
airplane, if removed, and do a test of the Spoiler/Speedbrake Control System. Close access.
Group 1-3, Configuration 2:
No work is necessary for these airplanes.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
119757-200, 757-200CB, 757-
200PF
Group 2:
Affected Maintenance Zones
ZoneModel
119757-300
Group 3:
Affected Maintenance Zones
ZoneModel
119757-200, 757-300
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2015-08-01 and Boeing Service
Bulletin 757-27A0152 are related to this Boeing Service Bulletin.
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Boeing recommends that the change given in this service bulletin be done within 90 days after the
original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this service bulletin for each
airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with
operator task hour data if necessary. The estimate does not include lost time. These are some examples
of lost time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to inspect the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
NOTE: The work in this service bulletin includes the removal and installation of the E3-1 electronics
shelf in the Main Equipment Center. The Manpower estimates that follow only include the
removal, installation and test of the flight Control System Electronics Unit (CSEU) modules.
If there are more modules installed on the E3-1 electronics shelf, that must be removed for
access, the estimates that follow must be increased, as applicable, to include all removals,
installations and tests.
Group 1, Configuration 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.503.002Open Access
0.400.401FIGURE 1
---FIGURE 2 (Wire Routing only)
1.201.201FIGURE 3
0.200.201FIGURE 4
1.001.001FIGURE 6
0.400.401FIGURE 7
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Group 1, Configuration 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.503.002Close Access
2.254.502Test
8.4513.70TOTAL FOR EACH AIRPLANE
Group 2-3, Configuration 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.503.002Open Access
0.400.401FIGURE 1
---FIGURE 2 (Wire Routing only)
1.201.201FIGURE 3
0.200.201FIGURE 5
1.001.001FIGURE 6
0.400.401FIGURE 7
1.503.002Close Access
2.254.502Test
8.4513.70TOTAL FOR EACH AIRPLANE
Group 1-3, Configuration 2:
None.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 54530 278RS
b. Boeing Service Bulletin 757-27A0152
c. Boeing Service Related Problem (SRP) 757-SRP-27-0290
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2015-08-01
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e. Service Bulletin Index D624N001
f. Standard Wiring Practices Manual (SWPM) 20-00-11, 20-00-14, 20-10-11, 20-10-12, 20-10-19,
20-20-00, 20-71-14
g. 757 Aircraft Maintenance Manual (AMM) 27-09-00, 27-61-00, 29-11-00
h. 757 Wiring Diagram Manual (WDM) 27-09-13, 27-61-13, 27-61-17
i. Boeing Multi-Operator Message (MOM) MOM-MOM-17-0685
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
27-09, 27-61757 Wiring Diagram Manual
27-41757 Illustrated Parts Catalog
27-61757 Aircraft Maintenance Manual
27-09, 27-61757 System Schematic Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 19

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page.
2. Fax to (206) 662-7145.
Group 1-3, Configuration 1:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the Original Is-
sue date of this
Service Bulletin
(US Dollars)
ROLT as of the
Original Issue
date of this Ser-
vice Bulletin
(Calendar Days)
QTYDateNameKit Number
$1380.00224(a)(a)TOP KIT - 757
SPOILER CON-
TROL MODULE
RELAYS
WIRING
CHANGE
012N8932-23
(a) At the time of the release of this service bulletin, spec release dates and quantities have not been deter-
mined. This information will be provided in an Information Notice when it becomes available.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
Group 1-3, Configuration 2:
None.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
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ALL
Kit 012N8932
NotesExisting Part
Number
NameQtyNew Part Number
-23
TOP KIT - 757
SPOILER CON-
TROL MODULE
RELAYS WIRING
CHANGE
-012N8932-23
ASSY W12651012N8932-101
INSULATION
SLEEVING, HEAT
SHRINKABLE,
YELLOW, IN DIA
3/32", CLASS 1
14829A9003-334
CONTACT, PIN12BACC47EF1
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number / Specifica-
tion
(a)LACING TAPE30 feetBMS 13-54, Type 3, Class 1
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data. Refer to Boeing Standard Wiring Practices Manual SWPM 20-10-11 for optional lacing tape.
Operators can also supply the following parts or materials to do the change in this service bulletin
instead of ordering the top kit. Parts and materials in the manuals given in Paragraph 1.J.,
References, can also be necessary. Examine operator part and material supply to make sure all
necessary parts and materials are available.
NotesNameQTYPart Number /
Specification
(a)Wiring6 ftBMS13-48, TYPE
10, CLASS 1,
GAUGE 22
(b)INSULATION SLEEVING, HEAT
SHRINKABLE, YELLOW, IN DIA
3/32", CLASS 1
14829A9003-334
(c)CONTACT, PIN12BACC47EF1
(a) Fabricate the wire kit in accordance with FIGURE 6 - WIRE KIT - CUT AND CODE TABLE.
Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-14 for optional wire.
(b) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-11 for optional sleeving.
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NotesNameQTYPart Number /
Specification
(c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are given in 757 SRM, Chapter 51
– Torque limits to tighten nuts and bolts are given in 757 SRM, Chapter 51
4. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements.
5. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
6. These work instructions refer to procedures included on other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
8. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
The removed part can be discarded if a new or serviceable part is installed.
9. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
10. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
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including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
Group 1-3, Configuration 1:
1. Open the circuit breakers that follow, attach circuit breaker collars and "DO-NOT-CLOSE" tags,
and make sure the system is in a zero energy state:
Group 1, Configuration 1:
NumberNamePanel / Location
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
Group 2, Configuration 1:
NumberNamePanel / Location
Airplanes without Yaw Damper / Stabilizer Trim Module
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
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Group 2, Configuration 1:
NumberNamePanel / Location
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
Airplanes with Yaw Damper / Stabilizer Trim Module
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
Group 3, Configuration 1:
NumberNamePanel / Location
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
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Group 3, Configuration 1:
NumberNamePanel / Location
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
2. Get access to the E3-1 electronics shelf in the Main Equipment Center.
3. Remove and keep the flight Control System Electronics Unit (CSEU) modules from E3-1 electronics
shelf if necessary. Refer to 757 AMM 27-09-00 as an accepted procedure.
4. Disconnect and stow all electrical connectors from the E3-1 electronics shelf disconnect bracket
AE0301. Refer to SWPM 20-10-11 as an accepted procedure.
5. Remove the E3-1 electronics shelf from the airplane if necessary, in accordance with FIGURE 1.
6. RC - Change the W1265 wire bundle in accordance with the below figures:
a. Group 1, Configuration 1:
FIGURE 2, FIGURE 3 and FIGURE 4.
b. Group 2-3, Configuration 1:
FIGURE 2, FIGURE 3 and FIGURE 5.
7. RC - Install the wire bundle to the Spoiler Control Modules M530 and M531 in accordance with
FIGURE 6.
8. Do a continuity check of the new and changed wires in the E3-1 electronics shelf.
9. If the E3-1 electronics shelf was removed, install the kept E3-1 electronics shelf to the airplane in
accordance with FIGURE 7.
10. Connect all electrical connectors to the E3-1 electronics shelf disconnect bracket AE0301. Refer
to SWPM 20-10-11 as an accepted procedure.
11. If the CSEU modules were removed, install the kept CSEU modules on E3-1 electronics shelf.
Refer to 757 AMM 27-09-00 as an accepted procedure.
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12. Close the circuit breakers that follow and remove the circuit breaker collars and the
"DO-NOT-CLOSE" tags:
Group 1, Configuration 1:
NumberNamePanel / Location
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
Group 2, Configuration 1:
NumberNamePanel / Location
Airplanes without Yaw Damper / Stabilizer Trim Module
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
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Group 2, Configuration 1:
NumberNamePanel / Location
C00566WARN ELEX BP11 / B18
Airplanes with Yaw Damper / Stabilizer Trim Module
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
Group 3, Configuration 1:
NumberNamePanel / Location
C01560YAW DAMPER LP11 / A18
C01017STAB TRIM CONT LP11 / C5 or
P11 / H11
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01031RUD RATIOP11 / D18 or
P11 / G10
C01025FLAP SLAT ELEC UNIT 1P11 / G12
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Group 3, Configuration 1:
NumberNamePanel / Location
C01037FLAP SLAT SENSOR ELEC UNIT 1P11 / G14
C00565WARN ELEX AP11 / J33
C00566WARN ELEX BP11 / B18
13. If the CSEU modules were removed, do the CSEU Modules Installation Test. Refer to 757 AMM
27-09-00 as an accepted procedure.
14. RC - Do the operational test of the Spoiler/Speedbrake Control System in accordance with the
instructions below:
MOVE ALL PERSONS AND EQUIPMENT AWAY FROM THE SPOILERS,
AND OTHER FLIGHT CONTROL SURFACES, DURING THE FOLLOWING
TEST STEPS. THE CONTROL SURFACES CAN MOVE QUICKLY AND
CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
WARNING
a. RC Exempt - Prepare for the test.
(1) Supply pressure to the left, right, and center hydraulic systems. Refer to 757 AMM
29-11-00 as an accepted procedure.
(2) Make sure the circuit breakers that follow are closed:
NumberNamePanel / Location
C01537CSEU 2L-AC orP11 / C8
FLT CONT ELEC 2L AC
C01534CSEU 1L-DC orP11 / C7
FLT CONT ELEC 1L DC
C01538CSEU 1L-AC orP11 / C6
FLT CONT ELEC 1L AC
C01533CSEU 2L-DC orP11 / C9
FLT CONT ELEC 2L DC
C01025FLAP SLAT ELEC UNIT 1 PWRP11 / G12
C01037FLAP SLAT ELEC UNIT 1 SENSORP11 / G14
(3) Make sure that the Speedbrake Lever is in its down-and-locked detent position.
(4) Set the Aileron Trim at 0 units.
(5) Set the Stabilizer Trim at the Green Band.
(6) Make sure the Control Wheel is in the neutral position.
(7) Make sure that the Control Wheel is free to move and responds to manual inputs, and is
not being affected by other input signals.
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b. Do the Control Wheel Input test that follows:
(1) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that all spoiler pairs except 4 and 9 respond to control wheel
commands. Refer to 757 AMM 27-61-00 for more data on spoiler controls.
(b) Do step (a) again two more times.
(2) Put the Flap Control Lever in the 20-unit detent.
(3) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that all spoiler pairs except 4 and 9 respond to control wheel
commands. Refer to 757 AMM 27-61-00 for more data on spoiler controls.
(b) Do step (a) again two more times.
(4) Put the Flap Control Lever in the 25-unit detent.
(5) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that all spoiler pairs except 4 and 9 respond to control wheel
commands. Refer to 757 AMM 27-61-00 for more data on spoiler controls.
(b) Do step (a) again two more times.
(6) Move the Speedbrake Lever to its up detent position.
(a) Make sure that spoiler pairs 1 and 12 and 5 and 8 move up along with other spoiler
panels.
(7) Put the Flap Control Lever in the 15-unit detent.
(8) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
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1) Make sure that all spoiler pairs stay up for speedbrake function and, except for
4 and 9, respond to control wheel commands. Refer to 757 AMM 27-61-00 for
more data on spoiler controls.
(b) Do step (a) again two more times.
(9) Move the Speedbrake Lever to its down-and-locked detent position.
(a) Make sure that all spoilers move down.
(10) Put the Flap Control Lever in the 25-unit detent.
(11) Move the Speedbrake Lever to its up detent position.
(a) Make sure that all spoilers move up.
(12) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that all spoiler pairs stay up for speedbrake function and, except for
4 and 9, respond to control wheel commands. Refer to 757 AMM 27-61-00 for
more data on spoiler controls.
(b) Do step (a) again two more times.
(13) Move the Speedbrake Lever to its down-and-locked detent position.
(a) Make sure that all spoilers move down.
(14) Remove the power from the right hydraulic system. Refer to 757 AMM 29-11-00 as an
accepted procedure.
(15) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that spoiler pairs 1 and 12, 5 and 8, and 3 and 10 respond to control
wheel commands. Refer to 757 AMM 27-61-00 for more data on spoiler controls.
NOTE: Other spoiler pairs will be inoperative due to removal of power from
the right hydraulic system.
(b) Do step (a) again two more times.
(16) Move the Speedbrake Lever to its up detent position.
(a) Make sure that spoiler pairs 1 and 12, 5 and 8, and 3 and 10 move up.
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NOTE: Other spoiler pairs will be inoperative due to removal of power from the right
hydraulic system.
(17) The time for the test that follows must be done in 16 seconds or less.
(a) Turn the control wheel from the neutral position fully clockwise then back to the
neutral position, then turn the control wheel from the neutral position fully
counter-clockwise then back to the neutral position.
1) Make sure that spoiler pairs 1 and 12, 5 and 8, and 3 and 10 stay up for
speedbrake function and respond to control wheel commands. Refer to 757
AMM 27-61-00 for more data on spoiler controls.
NOTE: Other spoiler pairs will be inoperative due to removal of power from
the right hydraulic system.
(b) Do step (a) again two more times.
(18) Move the Speedbrake Lever to its down-and-locked detent position.
(a) Make sure that spoiler pairs 1 and 12, 5 and 8, and 3 and 10 move down.
NOTE: Other spoiler pairs will be inoperative due to removal of power from the right
hydraulic system.
(19) Put the Flap Control Lever in the UP detent.
c. RC Exempt - Close up.
(1) Make sure the control wheels are in their neutral position.
(2) Make sure the Speedbrake Lever is in its down-and-locked detent position.
15. Put the airplane back to a serviceable condition.
Group 1-3, Configuration 2:
1. No work is necessary for these airplanes.
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 1.
• E3-1 ELECTRONICS
SHELF
E3 RACK
STANCHION
INBD
• TRAY
2802746
FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL
(SHEET 1 OF 3)
Original Issue: December 18, 2017
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PROPRIETARY - Copyright © Unpublished
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
Е3 RACK
STANCHION
E3 RACK
TRAY  STANCHION
TRAY.
INBD  INBD
ALTERNATE CONFIGURATION
E3 RACK
STANCHION
E3 RACK
STANCHION
INBD  INBD
A-A  2802911
(ROTATED 180 DEGREES)
FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL
(SHEET 2 OF 3)
Original Issue: December 18, 2017
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.

### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2NAS1801-4-11SCREWRemove / Keep1
2NAS1149D0432JWASHERRemove / Keep
(a)1BACN10YR3CDNUTRemove / Keep2
(a)1NAS1149D0316JWASHERRemove / Keep
(a)1BACW10P416ANWASHERRemove / Keep
(a)1BACB30NM3K3BOLTRemove / Keep
(a)1BACN10YR3CDNUTRemove / Keep3
(a)1BACW10P416ANWASHERRemove / Keep
(a)1NAS1149D0316JWASHERRemove / Keep
(a)1BACB30NM3K5BOLTRemove / Keep
(b)2BACN10YR3CDNUTRemove / Keep4
(b)2NAS1149D0316JWASHERRemove / Keep
(b)2BACW10P416ANWASHERRemove / Keep
(b)2BACB30NM3K5BOLTRemove / Keep
(b)2BACN10YR3CDNUTRemove / Keep5
(b)2BACW10P416ANWASHERRemove / Keep
(b)2NAS1149D0316JWASHERRemove / Keep
(b)2BACB30NM3K5BOLTRemove / Keep
1BACN10YR3CDNUTRemove / Keep6
1NAS1149D0316HWASHERRemove / Keep
1-JUMPERRemove / Keep
From airplane.1-E3-1 ELECTRONIC
SHELF
Remove / Keep7
(a) This step is only applicable if an alternate configuration is not installed.
(b) This step is only applicable if an alternate configuration is installed.
FIGURE 1: E3-1 ELECTRONICS SHELF - REMOVAL
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 1.
ABC
MAIN EQUIPMENT CENTER
M531
M530
00
TB109
E3-1 ELECTRONICS SHELF
TYPICAL
2802921
FIGURE 2: W1265 WIRE BUNDLE ROUTING
(SHEET 1 OF 3)
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Work - See page 1 for details.  36 of 49

### Page 37 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
M531
M530
TB169
E3-1 ELECTRONICS SHELF
(TYPICAL)
(ALTERNATIVE CONFIGURATION FOR
GROUP 2 ONLY)
2802924
FIGURE 2: W1265 WIRE BUNDLE ROUTING
(SHEET 2 OF 3)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
M531
M530
TB169
E3-1 ELECTRONICS SHELF
(TYPICAL)
(ALTERNATIVE CONFIGURATION FOR
GROUP 3 ONLY)
C  2802928
FIGURE 2: W1265 WIRE BUNDLE ROUTING
(SHEET 3 OF 3)
Original Issue: December 18, 2017
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 1.
W1265  6 PLACES
SM21  -2061B-22-  A4  757 PROG A
-2061R-22-  B5  PROG SELECT A
D635A
SM22  -2062B-22-  A5  757 PROG B
-2062R-22-  B6  PROG SELECT B
LSM23  -2063B-22-  A13  757 PROG C
-2063R-22  B14  PROG SELECT C
D635B
K10876  M530  SPOILER CONT
MODULE 1 L
6 PLACES
X  -2067B-22  -2067R-22-  A4  B5  PROG SELECT A  757 PROG A
D637A
-2068B-22  A5  757 PROG B
-2068R-22  B6  PROG SELECT B
-2069B-22  A13  757 PROG C
110  -2069R-22HHHA B14 PROG SELECT C
D11726  D637B
K10878
M531  SPOILER CONT
MODULE 2 L
E3-1 SHELF
• ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING
EXISTING WIRE
FLAG NOTE
FIGURE 3: W1265 WIRE BUNDLE CHANGES
(SHEET 1 OF 2)
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### Page 40

REFERENCE: 757 WDM 27-61-13, 757 WDM 27-61-17.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationName
Flag
Note
(a)(b)12829A9003-334INSULATION SLEEVING, HEAT SHRINKABLE,
YELLOW, IN DIA 3/32", CLASS 1
1
(a) Cap and stow wires connectors D635B and D637B. Refer to SWPM 20-10-11 as an accepted procedure.
(b) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-11 for optional sleeving.
FIGURE 3: W1265 WIRE BUNDLE CHANGES
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 41

This Figure applies only to: Group 1, Configuration 1.
REFERENCE: 757 WDM 27-09-13, 757 WDM 27-61-13.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationName
Flag
Note
(a)(b)2829A9003-334INSULATION SLEEVING, HEAT SHRINKABLE,
YELLOW, IN DIA 3/32", CLASS 1
1
(a) Cap and stow wires terminal block TB109. Refer to SWPM 20-10-11 as an accepted procedure.
(b) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-11 for optional sleeving.
FIGURE 4: W1265 WIRE BUNDLE CHANGES
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 42

This Figure applies only to: Group 2-3, Configuration 1.
REFERENCE: 757 WDM 27-09-13, 757 WDM 27-61-13.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationName
Flag
Note
(a)(b)2829A9003-334INSULATION SLEEVING, HEAT SHRINKABLE,
YELLOW, IN DIA 3/32", CLASS 1
1
(a) Cap and stow wires near terminal block TB169. Refer to SWPM 20-10-11 as an accepted procedure.
(b) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-11 for optional sleeving.
FIGURE 5: W1265 WIRE BUNDLE CHANGES
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 1.
1 W1265
› 6 PLACES
757 PROG A  -0130-22-
PROG SELECT A
PROG SELECT B
757 PROG C  A13  -0504-22-
PROG SELECT C  B14
D635B
M530  SPOILER CONT
MODULE 1 L
PROG SELECT A
757 PROG B  A5  0142-22-
PROG SELECT B  B6
757 PROG C  A13
PROG SELECT C  B14
M531  SPOILER CONT
MODULE 2 L
E3-1 SHELF
- ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING
- EXISTING WIRE
→ FLAG NOTE  2802956
FIGURE 6: W1265 WIRE BUNDLE CHANGES
(SHEET 1 OF 2)
Original Issue: December 18, 2017
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### Page 44

REFERENCE: 757 WDM 27-61-13, 757 WDM 27-61-17.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationName
Flag
Note
(a)(b)1012N8932-101ASSY W12651
To tie wire bundle. Refer to SWPM
20-10-11 as an accepted proce-
dure. (b)
-BMS 13-54, TYPE 3,
CLASS 1
LACING TAPE
Refer to SWPM 20-71-14 as an
accepted procedure.
12BACC47EF1CONTACT, PIN2
(a) If additional wire is required, it is acceptable to use BMS13-48, TYPE 10, CLASS 1, GAUGE 22 wire.
(b) Refer to Boeing Standard Wiring Practices Manual SWPM 20-00-14 for optional wire and SWPM 20-10-
11 for optional lacing tape.
WIRE KIT - CUT AND CODE
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAUGE
COLOR
WIRE#WBA#
(a)BMS13-48, TYPE 10, CLASS 112PA220130W1265
(a)BMS13-48, TYPE 10, CLASS 112PA220142W1265
(a)BMS13-48, TYPE 10, CLASS 112PA220346W1265
(a)BMS13-48, TYPE 10, CLASS 112PA220350W1265
(a)BMS13-48, TYPE 10, CLASS 112PA220504W1265
(a)BMS13-48, TYPE 10, CLASS 112PA220515W1265
(a) Mark wire with wire number. Refer to SWPM 20-10-11 as an accepted procedure
FIGURE 6: W1265 WIRE BUNDLE CHANGES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 1.
• E3-1 ELECTRONICS
SHELF
E3 RACK
STANCHION
INBD
• TRAY
2802935
FIGURE 7: E3-1 ELECTRONICS SHELF - INSTALLATION
(SHEET 1 OF 4)
Original Issue: December 18, 2017
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
E3 RACK
STANCHION
E3 RACK
TRAY  STANCHION
TRAY.
INBD
ALTERNATE CONFIGURATION
E3 RACK
STANCHION
E3 RACK
STANCHION
INBD  INBD
A-A  B-B  2802943
(ROTATED 180 DEGREES)  (ROTATED 180 DEGREES)
FIGURE 7: E3-1 ELECTRONICS SHELF - INSTALLATION
(SHEET 2 OF 4)
Original Issue: December 18, 2017
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Work - See page 1 for details.  46 of 49

### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
To the airplane.1-E3-1 ELECTRONIC
SHELF
Install (Changed)1
2NAS1149D0432JWASHERInstall (Kept)2
2NAS1801-4-11SCREWInstall (Kept)
Install bolt head near
side. (a)
1BACB30NM3K3BOLTInstall (Kept)3
Under bolt head. (a)1BACW10P416ANWASHERInstall (Kept)
Under nut. (a)1NAS1149D0316JWASHERInstall (Kept)
(a)(c)1BACN10YR3CDNUTInstall (Kept)
Install bolt head far
side. (a)
1BACB30NM3K5BOLTInstall (Kept)4
Under bolt head. (a)1NAS1149D0316JWASHERInstall (Kept)
Under nut. (a)1BACW10P416ANWASHERInstall (Kept)
(a)(c)1BACN10YR3CDNUTInstall (Kept)
Install bolt head near
side. (b)
2BACB30NM3K5BOLTInstall (Kept)5
Under bolt head. (b)2BACW10P416ANWASHERInstall (Kept)
Under nut. (b)2NAS1149D0316JWASHERInstall (Kept)
(b)(c)2BACN10YR3CDNUTInstall (Kept)
Install bolt head far
side. (b)
2BACB30NM3K5BOLTInstall (Kept)6
Under bolt head. (b)2NAS1149D0316JWASHERInstall (Kept)
Under nut. (b)2BACW10P416ANWASHERInstall (Kept)
(b)(c)2BACN10YR3CDNUTInstall (Kept)
1-JUMPERInstall (Kept)7
1NAS1149D0316HWASHERInstall (Kept)
1BACN10YR3CDNUTInstall (Kept)
FIGURE 7: E3-1 ELECTRONICS SHELF - INSTALLATION
(SHEET 3 OF 4)
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 48

More DataQtyIdentificationNameTaskStep
Between the E3-1
electronic shelf and
the airplane struc-
ture. Refer to SWPM
20-20-00 as an ac-
cepted procedure.
(d)
--RESISTANCEMeasure8
(a) This step is only applicable if an alternate configuration is not installed.
(b) This step is only applicable if an alternate configuration is installed.
(c) Torque nut from a minimum 45 inch-pounds to a maximum 55 inch-pounds.
(d) Make sure that the resistance measurement is not more than 0.0005 ohms (0.5 milliohms). If the resistance
measurement is more than 0.0005 ohms (0.5 milliohms), remove the E3-1 electronic shelf, clean the
faying surfaces and measure the bonding resistance again. Refer to SWPM 20-20-00 as an accepted
procedure.
FIGURE 7: E3-1 ELECTRONICS SHELF - INSTALLATION
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN 757-27A0157
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 757-27A0157
ALERT  ALERT
Boeing Part Demand Intent
After review of this service bulletin, Boeing asks that the primary engineer fill out this survey to help Boeing
predict the quantity and timing of the Boeing supplied kits.
Airline:
Contact Name:
Date:
Contact E-mail:
• Yes  - No Have/will you recommend to your airline to accomplish this service bulletin?
• Yes - No Would issuance of an AD change this decision?
When would you likely be starting this SB incorporation? Month/ Year_
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes
For inspection Service Bulletins, are you planning to replace on condition, or a fleet campaign to replace on
all airplanes regardless of condition?
- On Condition  Campaign
If you are not incorporating this Service Bulletin at this time will you please help us understand the reason(s)
why? Your input will help us provide better customer support.
- Cost Prohibitive  Continue Inspections  • Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to:
sbsolutions@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not
constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute  2326214
a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
APPENDIX A:
(SHEET 1 OF 1)
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